EP1641952B1 - Alliage al-cu-mg-ag-mn destine a des applications structurales necessitant une resistance et une ductilite ameliorees - Google Patents

Alliage al-cu-mg-ag-mn destine a des applications structurales necessitant une resistance et une ductilite ameliorees Download PDF

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Publication number
EP1641952B1
EP1641952B1 EP04753336.9A EP04753336A EP1641952B1 EP 1641952 B1 EP1641952 B1 EP 1641952B1 EP 04753336 A EP04753336 A EP 04753336A EP 1641952 B1 EP1641952 B1 EP 1641952B1
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EP
European Patent Office
Prior art keywords
aluminum alloy
alloy according
alloy
mpa
sample
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Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
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EP04753336.9A
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German (de)
English (en)
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EP1641952A4 (fr
EP1641952A2 (fr
Inventor
Alex Cho
Vic Dangerfield
Bernard Bes
Timothy Warner
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Constellium Issoire SAS
Constellium Rolled Products Ravenswood LLC
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Constellium Issoire SAS
Constellium Rolled Products Ravenswood LLC
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Publication of EP1641952A4 publication Critical patent/EP1641952A4/fr
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    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C21/00—Alloys based on aluminium
    • C22C21/12—Alloys based on aluminium with copper as the next major constituent
    • C22C21/16—Alloys based on aluminium with copper as the next major constituent with magnesium
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
    • C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
    • C22F1/04—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon
    • C22F1/057—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon of alloys with copper as the next major constituent

Definitions

  • the present invention relates generally to aluminum-copper-magnesium based alloys and products, and more particularly to aluminum-copper-magnesium alloys and products containing silver, including those particularly suitable for aircraft structural applications requiring high strength and ductility as well as high durability and damage tolerance such as fracture toughness and fatigue resistance.
  • Aerospace applications generally require a very specific set of properties.
  • High strength alloys are generally desired, but according to the desired intended use, other properties such as high fracture toughness or ductility, as well as good corrosion resistance may also usually be required.
  • Aluminum alloys containing copper, magnesium and silver are known in the art.
  • US Patent No. 4,772,342 describes a wrought aluminum-copper-magnesium-silver alloy including copper in an amount of 5-7 weight (wt.) percent (%), magnesium in an amount of 0.3-0.8 wt.%, silver in an amount of 0.2-1 wt. %, manganese in an amount of 0.3 - 1.0 wt.%, zirconium in an amount of 0.1 - 0.25 wt.%, vanadium in an amount of 0.05 - 0.15 wt. %, silicon less than 0.10 wt. %, and the balance aluminum.
  • US Patent No. 5,376,192 discloses a wrought aluminum alloy comprising about 2.5-5.5 wt. % copper, about 0.10 - 2.3 wt. % magnesium, about 0.1-1% wt. % silver, up to 0.05 wt.% titanium, and the balance aluminum, in which the amount of copper and magnesium together is maintained at less than the solid solubility limit for copper and magnesium in aluminum.
  • US Patent Nos. 5,630,889 , 5,665,306 , 5,800,927 , and 5,879,475 disclose substantially vanadium-free aluminum-based alloys including about 4.85-5.3 wt.% copper, about 0.5-1 wt.% magnesium, about 0.4-0.8 wt.% manganese, about 0.2 - 0.8 wt.% silver, up to about 0.25 wt.% zirconium, up to about 0.1 wt.% silicon, and up to 0.1 wt.% iron, the balance aluminum, incidental elements and impurities.
  • the alloy can be produced for use in extruded, rolled or forged products, and in a preferred embodiment, the alloy contains a Zr level of about 0.15 wt.%.,
  • An object of the present invention was to provide a high strength, high ductility alloy, comprising copper, magnesium, silver, manganese and optionally titanium, which is substantially free of zirconium. Certain alloys of the present invention are particularly suitable for a wide range of aircraft applications, in particular for fuselage applications, lower wing skin applications, and/or stringers as well as other applications.
  • an aluminum-copper alloy comprising about 3.5-5.8 wt.% copper, 0.1 - 1.8 wt.% magnesium, 0.2 -0.8 wt.% silver, 0.1-0.8 wt.% manganese, as well as 0.02 - 0.12 wt.% titanium and the balance being aluminum and incidental elements and impurities. These incidental elements impurities can optionally include iron and silicon.
  • one or more elements selected from the group consisting of chromium, hafnium, scandium and vanadium may be added in an amount of up to 0.8 wt.% for Cr, 1.0 wt.% for Hf, 0.8 wt.% for Sc, and 0.15 wt.% for V, either in addition to, or instead of Ti.
  • An alloy according to the present invention is substantially free of zirconium. This means that zirconium is preferably present in an amount of less than or equal to about 0.05 wt.%, which is the conventional impurity level for zirconium.
  • inventive alloy can be manufactured and/or treated in any desired manner, such as by forming an extruded, rolled or forged product.
  • present invention is further directed to methods for the manufacture and use of alloys as well as to products comprising alloys.
  • the invention is defined in the appended claims.
  • Structural members for aircraft structures whether they are extruded, rolled and/or forged, usually benefit from enhanced strength.
  • alloys with improved strength, combined with high ductility are particularly suitable for designing structural elements to be used in fuselages as an example.
  • the present invention fulfills a need of the aircraft industry as well as others by providing an aluminum alloy, which comprises certain desired amounts of copper, magnesium, silver, manganese and titanium and/or other grain refining elements such as chromium, hafnium, scandium, or vanadium, and which is also substantially free of zirconium.
  • substantially zirconium free means a zirconium-content equal to or below about 0.05 wt.%, preferably below about 0.03 wt.%, and still more preferably below about 0.01 wt.%.
  • the present invention relates to alloys comprising (i) between 3.5 wt.% and 5.8 wt.% copper, preferably between 3.80 and 5.5 wt.%, and still more preferably between 4.70 and 5.30 wt.%, (ii) between 0.1 wt% and 0.8 wt.% silver, and (iii) between 0.1 - 1.8 wt.% of magnesium, preferably between 0.2 and 1.5 wt.%, more preferably between 0.2 and 0.8 wt.%, and still more preferably between 0.3 and 0.6 wt.%.
  • manganese and titanium and/or other grain refining elements enhanced the strength and ductility of such Al-Cu-Mg-Ag alloys.
  • manganese is included in an amount of about 0.1 to 0.8 wt.%, and particularly preferably in an amount of about 0.3 to 0.5 wt.%.
  • Titanium is advantageously included in an amount of about 0.02 to 0.12 wt.%, preferably 0.03 to 0.09 wt.%, and more preferably between 0.03 and 0.07 wt.%.
  • grain refining elements can comprise, for example, Cr in an amount of about 0.1 to 0.8 wt.%, Sc in an amount of about 0.03 to 0.6 wt.%, Hf in an amount of 0.1 to about 1.0 wt.% and/or V in an amount of about 0.05 to 0.15 wt.%,
  • the sheet or plate according to the claims is particularly suitable for the manufacture of fuselage skin for an aircraft or other similar or dissimilar article. It can also be used, for example for the manufacture of wing skin for an aircraft or the like.
  • a product of the present invention exhibits unexpectedly improved fracture toughness and fatigue crack propagation rate, as well as a good corrosion resistance and mechanical strength after solution heat treatment, quenching, stretching and aging.
  • a sheet or plate product of the present invention preferably has a thickness ranging from about 2 mm to about 10 mm, and preferably has a fracture toughness K C , determined at room temperature from the R-curve measure on a 406 mm wide CCT panel in the L-T orientation, which equals or exceeds about 170 MPa ⁇ m, and preferably exceeds 180 or even 190 MPa ⁇ m.
  • sheet and “plate” are interchangeable.
  • Sheet and plate in the thickness range from about 5 mm to about 25 mm advantageously have an elongation of at least about 13.5 % and a UTS of at least about 69.5 ksi (479.2 MPa), and/or an elongation of at least about 15.5% and a UTS of at least about 69 ksi (475.7 MPa).
  • elongation and UTS values of the product may decrease slightly.
  • the instant UTS and elongation properties are deduced from a tensile test in the L-direction as is commonly utilized in the industry.
  • inventive alloy is superior to alloys considered to be the closest prior art.
  • material performance of the inventive alloy is therefore expected to be superior to that of other prior art alloys for a myriad and broad range of wrought product forms and gauges.
  • the addition of scandium in the range of 0.03 - 0.25 wt.% is particularly preferred in some embodiments.
  • compositions may include normal and/or inevitable impurities, such as silicon, iron and zinc.
  • the aging treatment is usually of a high importance, as it aims at obtaining a good corrosion behavior, without losing too much strength.
  • Different aging practices tested for all three alloys were the following:
  • Alloy A according to the invention exhibits better strength and elongation than the other alloys B and C, which do not contain Mn and/or Ti.
  • the present invention further shows a significant improvement of UTS (ultimate tensile strength), TYS (tensile yield strength) and E (elongation) at peak strength.
  • Alloy A according to the invention exhibits better strength and elongation than the other alloys B and C, which do not contain Mn and/or Ti.
  • the present invention further shows a significant improvement of UTS (ultimate tensile strength), TYS (tensile yield strength) and E (elongation) at peak strength.
  • Alloy A sample is also evident by Scanning Electron Microscopy examination on the fractured surfaces of these fracture test specimens.
  • the fractography of Alloy A sample in Figure 1 shows the fractured surfaces with ductile fracture mode while that of Alloy B sample in Figure 2 shows many areas of brittle fracture mode.
  • the scalped ingots were heated to 500°C and hot rolled with an entrance temperature of 480°C on a reversible hot rolling mill until a thickness of 20 mm was reached, followed by hot rolling on a tandem mill until a thickness of 4.5 mm was reached.
  • the strip was coiled at a metal temperature of about 280°C. The coil was then cold-rolled without intermediate annealing to a thickness of 3.2 mm.
  • Solution heat treatment was performed at 530°C during 40 minutes, followed by quenching in cold water (water temperature comprised between 18 and 23°C).
  • Stretching was performed with a permanent set of about 2%.
  • Fracture toughness was calculated from the R-curves determined on CCT-type test pieces of a width of 760 mm with a ratio of crack length a / width of test piece W of 0.33.
  • sample S (without zirconium) has significantly higher K C values than the zirconium-containing sample P.
  • Exfoliation corrosion was determined by using the EXCO test (ASTM G34) on sheet samples in the T8 temper. Both samples P and S were rated EA.
  • Intercrystalline corrosion was determined according to ASTM B 110 on sheet samples in the T8 temper. Results are summarized on table 10. As illustrated in table 9, sample S shows generally shallower corrosive attack, and specifically lower maximum depths of intergranular attack than sample P. The total number of corrosion sites observed in sample S was nevertheless greater. It should be noted that the impact of IGC sensitivity on in service properties is generally considered to be related to the role of corroded sites as potential sites for fatigue initiation. In this context, the shallower attack observed on sample S would be considered advantageous.

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  • Chemical & Material Sciences (AREA)
  • Mechanical Engineering (AREA)
  • Organic Chemistry (AREA)
  • Metallurgy (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Crystallography & Structural Chemistry (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • Metal Rolling (AREA)
  • Conductive Materials (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Heat Treatment Of Steel (AREA)

Claims (18)

  1. Alliage d'aluminium ayant une résistance et une ductilité améliorées, comprenant :
    a) 4,70 à 5,30 % en poids de Cu
    0,3 à 0,6 % en poids de Mg
    0,3 à 0,5 % en poids de Mn
    0,1 à 0,8 % en poids Ag
    0,02 à 0,12 % en poids de Ti et
    optionnellement un ou plusieurs éléments sélectionnés dans le groupe constitué de 0,1 à 0,8 % en poids de Cr, 0,1 à 1,0 % en poids de Hf, 0,03 à 0,6 % en poids de Sc et 0,05 à 0,15 % en poids de V,
    b) le reste étant de l'aluminium et des éléments et impuretés normaux et/ou inévitables,
    et dans lequel ledit alliage est sensiblement exempt de zirconium, c'est-à-dire que la teneur en Zr est inférieure ou égale à 0,05 % en poids.
  2. Alliage d'aluminium selon la revendication 1, comprenant de 0,03 à 0,09 % en poids de Ti.
  3. Alliage d'aluminium selon la revendication 2, dans lequel Ti est de 0,03 à 0,07 % en poids.
  4. Alliage d'aluminium selon la revendication 1, comprenant de 0,1 à 0,6 % en poids de Ag.
  5. Alliage d'aluminium selon la revendication 4, dans lequel Ag est de 0,2 à 0,5 % en poids.
  6. Alliage d'aluminium selon la revendication 1, comprenant de 0,03 à 0,25 % en poids de Sc.
  7. Alliage d'aluminium selon la revendication 1, comprenant de 0,1 à 1,0 % en poids de Hf.
  8. Alliage d'aluminium selon la revendication 1, comprenant de 0,05 à 0,15 % en poids de V.
  9. Alliage d'aluminium selon la revendication 1, comprenant de 0,1 à 0,8 % en poids de Cr.
  10. Alliage d'aluminium selon la revendication 1, dans lequel Cu est de 4,70 à 5,20 % en poids.
  11. Alliage d'aluminium selon la revendication 1, dans lequel le Zr est inférieur à 0,03 % en poids.
  12. Alliage d'aluminium selon la revendication 1, dans lequel le Zr est inférieur à 0,01 % en poids.
  13. Alliage d'aluminium selon l'une quelconque des revendications 1 à 12, qui a été traité thermiquement en solution, trempé, stabilisé et/ou vieilli artificiellement.
  14. Produit de tôle d'alliage d'aluminium d'une épaisseur allant de 5 à 25 mm selon la revendication 10, ayant au moins une propriété mécanique (direction L) sélectionnée dans le groupe constitué :
    a) d'un allongement d'au moins 13,5 % et une résistance à la traction d'au moins 69,5 ksi (479,2 MPa) et
    b) d'un allongement d'au moins 15,5 % et une résistance à la traction d'au moins 69 ksi (475,7 MPa).
  15. Élément structural approprié pour une utilisation dans la construction d'aéronefs comprenant un alliage d'aluminium selon l'une quelconque des revendications 1 à 14.
  16. Produit corroyé comprenant un alliage d'aluminium selon l'une quelconque des revendications 1 à 14.
  17. Procédé de production d'un élément structural d'aéronef comprenant l'utilisation d'un alliage selon l'une quelconque des revendications 1 à 14.
  18. Tôle comprenant un alliage d'aluminium qui est sensiblement exempt de zirconium selon la revendication 1, ladite tôle ayant une épaisseur allant de 2 mm à 10 mm, et une résistance à la rupture KC, déterminée à température ambiante à partir de la mesure de la courbe R sur un panneau préfissuré au centre dans l'orientation L-T d'une largeur de 406 mm, qui est supérieure ou égale à 170 MPa√m, et de la vitesse de propagation des fissures déterminée selon la norme ASTM E 647 sur un échantillon préfissuré au centre ayant une largeur de 400 mm, à une résistance R d'amplitude constante = 0,1 qui est inférieure ou égale à 3,0 10-2 mm/cycle à ΔK = 60 MPa√m.
EP04753336.9A 2003-05-28 2004-05-26 Alliage al-cu-mg-ag-mn destine a des applications structurales necessitant une resistance et une ductilite ameliorees Expired - Lifetime EP1641952B1 (fr)

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Application Number Priority Date Filing Date Title
US47353803P 2003-05-28 2003-05-28
PCT/US2004/016493 WO2004106566A2 (fr) 2003-05-28 2004-05-26 Alliage al-cu-mg-ag-mn destine a des applications structurales necessitant une resistance et une ductilite ameliorees

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EP1641952A2 EP1641952A2 (fr) 2006-04-05
EP1641952A4 EP1641952A4 (fr) 2014-08-06
EP1641952B1 true EP1641952B1 (fr) 2018-07-11

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US (2) US7229508B2 (fr)
EP (1) EP1641952B1 (fr)
BR (1) BRPI0410713B1 (fr)
CA (1) CA2523674C (fr)
DE (1) DE04753336T1 (fr)
WO (1) WO2004106566A2 (fr)

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US7547366B2 (en) * 2004-07-15 2009-06-16 Alcoa Inc. 2000 Series alloys with enhanced damage tolerance performance for aerospace applications
US8083871B2 (en) 2005-10-28 2011-12-27 Automotive Casting Technology, Inc. High crashworthiness Al-Si-Mg alloy and methods for producing automotive casting
WO2008110270A1 (fr) * 2007-03-09 2008-09-18 Aleris Aluminum Koblenz Gmbh Alliage d'aluminium présentant une résistance élevée à haute température
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CA2707311C (fr) 2007-12-04 2017-09-05 Alcoa Inc. Alliages d'aluminium-cuivre-lithium ameliores
US8333853B2 (en) * 2009-01-16 2012-12-18 Alcoa Inc. Aging of aluminum alloys for improved combination of fatigue performance and strength
EP2389458B1 (fr) 2009-01-22 2015-09-16 Alcoa Inc. Alliages améliorés d'aluminium-cuivre contenant du vanadium
US9347558B2 (en) 2010-08-25 2016-05-24 Spirit Aerosystems, Inc. Wrought and cast aluminum alloy with improved resistance to mechanical property degradation
JP2013542320A (ja) 2010-09-08 2013-11-21 アルコア インコーポレイテッド 改良された６ｘｘｘアルミニウム合金及びその製造方法
US20120261039A1 (en) * 2011-03-07 2012-10-18 Alex Cho Method for manufacturing of vehicle armor components requiring severe forming with very high bend angles with very thick gauge product of high strength heat treatable aluminum alloys
ES2565482T3 (es) 2011-08-17 2016-04-05 Otto Fuchs Kg Aleación de Al-Cu-Mg-Ag resistente al calor, así como procedimiento para la fabricación de un producto semiacabado o producto a partir de una aleación de aluminio de este tipo
WO2013172910A2 (fr) 2012-03-07 2013-11-21 Alcoa Inc. Alliages d'aluminium 2xxx améliorés et procédés de production correspondants
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CN109890663B (zh) 2016-08-26 2023-04-14 形状集团 用于横向弯曲挤压成形铝梁从而温热成型车辆结构件的温热成型工艺和设备
CA3040622A1 (fr) 2016-10-24 2018-05-03 Shape Corp. Procede de formage et de traitement thermique d'un alliage d'aluminium en plusieurs etapes pour la production de composants pour vehicules
CN108103373B (zh) * 2017-12-28 2019-11-19 中南大学 一种含银Al-Cu-Mg合金及获得高强度P织构的热处理方法
CN108504915B (zh) * 2018-05-02 2020-02-11 中南大学 一种具有高强度Goss+P织构和优异抗疲劳性能的Al-Cu-Mg合金及工艺
FR3087206B1 (fr) 2018-10-10 2022-02-11 Constellium Issoire Tôle en alliage 2XXX à haute performance pour fuselage d’avion
WO2020123096A2 (fr) * 2018-11-16 2020-06-18 Arconic Inc. Alliages d'aluminium 2xxx
CN111424200B (zh) * 2020-04-23 2021-10-08 西安交通大学 一种高强高耐热低钪银添加的Al-Cu-Mg系合金及其热处理工艺
CN112662969A (zh) * 2020-12-04 2021-04-16 中南大学 一种提高变形态铝铜镁银合金高温持久性能的热处理方法
FR3118065B1 (fr) 2020-12-18 2023-11-10 Constellium Issoire Produits corroyés en alliage 2xxx présentant une résistance à la corrosion optimisée et procédé d’obtention

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Publication number Publication date
EP1641952A4 (fr) 2014-08-06
US7229508B2 (en) 2007-06-12
US20070131313A1 (en) 2007-06-14
BRPI0410713A (pt) 2006-06-13
CA2523674C (fr) 2015-01-13
EP1641952A2 (fr) 2006-04-05
CA2523674A1 (fr) 2004-12-09
US20050084408A1 (en) 2005-04-21
DE04753336T1 (de) 2006-11-30
WO2004106566A3 (fr) 2005-02-10
BRPI0410713B1 (pt) 2018-04-03
US7704333B2 (en) 2010-04-27
WO2004106566A2 (fr) 2004-12-09

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